CN109848422A - The heat treatment method of precinct laser fusion forming GH4169 alloy - Google Patents
The heat treatment method of precinct laser fusion forming GH4169 alloy Download PDFInfo
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- CN109848422A CN109848422A CN201910138033.5A CN201910138033A CN109848422A CN 109848422 A CN109848422 A CN 109848422A CN 201910138033 A CN201910138033 A CN 201910138033A CN 109848422 A CN109848422 A CN 109848422A
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Abstract
The heat treatment method of precinct laser fusion of the present invention forming GH4169 alloy is shaped using precinct laser fusion, is configured to GH4169 alloy sample by precinct laser fusion 3D printing, is then homogenized, is dissolved and double aging is heat-treated respectively in heat-treatment furnace.The present invention homogenizes sample, solid solution and double aging heat treatment, there can be the hardening constituents such as δ phase γ ' and γ " in sample material, interdendritic brittleness Laves phase can be dissolved simultaneously, and make hardening constituent disperse educt on matrix, so as to improve the intensity of material, reduce material notch sensitivity, so that the comprehensive performance of material is improved, it solves hardening constituent caused by cooling rate is too fast in SLM forming process to be precipitated very few or be unevenly distributed, also overcome microfissure present in SLM forming GH4169 alloy, hole formation, metallurgical bonding is bad, the defects of powder is not completely melt.
Description
Technical field
The present invention relates to the heat treatment methods of precinct laser fusion forming GH4169 alloy, particularly belong to increases material manufacturing technology
In SLM technology and high temperature alloy technical field of heat treatment.
Background technique
GH4169 alloy is the alloy that China carries out that Development and design goes out based on Incone1718 alloy.It is a kind of iron-
The wrought superalloy of nickel-chrome base, alloy structure is by γ matrix, δ phase, carbide and hardening constituent γ ' (Ni3 (Al, Ti, Nb))
With γ " (Ni3Nb) composition, is widely applied within the temperature range of -253-650 DEG C, instantaneously using temperature up to 800 DEG C,
The unique design of alloy of GH4169 makes it have good comprehensive performance, i.e., high-intensitive, creep resistance and fatigue life, special
Be not 650 DEG C at a temperature of, mechanical property is with good stability.Many components of modern aeroengine, example
Such as turbine disk, casing, axis, stator, is obturaged, supporting element, pipeline, fastener blade, is all made of GH4169.Such as Taihang
For the alloy part number applied in engine up to 261, part gross weight accounts for 30% or more engine weight, accounts for core engine weight
60% .Since the part major part shape of aircraft engine is more complicated, using traditional processing technology (casting technique, forging
Technique, powder metallurgical technique), it is relatively low to shape relatively difficult and stock utilization.Therefore added using metal increases material manufacturing technology
The such alloy part of work is undoubtedly an important breakthrough.Although being easy to the such conjunction of Quick-forming by metal increases material manufacturing technology
Metal parts, but the factor for influencing manufacturing process precision is very much, such as physics and chemical property, the laser function of metal powder
Rate, spot diameter, defocus rate, scanning speed etc..These factors can all influence finally shaped alloy part performance, such as can allow
Part generates various defects, such as warpage, crackle, stomata, consistency are unevenly, secondly because in aircraft engine work
These parts also have different requirements, such as some parts pair to the performance of its own due to force way difference when work
The intensity requirement of itself is than high, some parts are relatively high to shock resistance requirement, some parts require to compare to comprehensive performance
It is high.Therefore it is necessary using suitable post processing mode.
Summary of the invention
It is an object of that present invention to provide a kind of precinct laser fusion forming GH4169 alloy heat treatment method, to SLM at
The performance of the GH4169 alloy part of shape is improved, for the part that works in varying environment to its own performance requirement not
It is same to propose different heat treatment modes.
The heat treatment method of precinct laser fusion forming GH4169 alloy of the present invention is using precinct laser fusion at uniformly
Change, the mode that solid solution and double aging heat treatment combine, specifically includes the following steps:
Step 1:
Slicing delamination is carried out to GH4169 alloy bulk sample threedimensional model, every layer of three-dimensional data is converted into 2-D data,
3D printing equipment is imported, 3D printing parameter is set, is shaped using precinct laser fusion, by high-purity GH4169 powder printing-forming
For 20mm × 20mm × 20mm square bulk sample；
The 3D printing parameter of setting: laser power 300W, scanning speed 1.3m/s, 150 μm of sweep span, scan path are upper and lower
Phase angle be 65 ° S type path, face powder 25 μm of thickness；
Step 2: in heat-treatment furnace, step 1 sample is homogenized respectively, be dissolved and double aging heat treatment；At homogenization
Manage process conditions are as follows: temperature control is 1010 ~ 1065 DEG C, keeps the temperature 1h；Solid solution treatment process condition are as follows: be air-cooled to 950 ~ 980 DEG C
Afterwards, 1h is kept the temperature；Double aging heat treatment condition are as follows: be air-cooled to 720 DEG C, keep the temperature 8h；Control 50 DEG C/h cooling velocity, heat treatment
620 DEG C are furnace-cooled to, after keeping the temperature 8h, is air-cooled to room temperature.
Beneficial effects of the present invention: the present invention homogenizes sample, is dissolved and double aging heat treatment, in sample material
Can have the hardening constituents such as δ phase γ ' and γ ", while interdendritic brittleness Laves phase can be dissolved, and make hardening constituent on matrix more
It dissipates and is precipitated, so as to improve the intensity of material, reduce material notch sensitivity, so that the comprehensive performance of material is improved, solution
Hardening constituent is precipitated very few or is unevenly distributed caused by cooling rate is too fast in SLM forming process of having determined, and also overcomes SLM forming
Microfissure present in GH4169 alloy, hole formation, the defects of metallurgical bonding is bad, powder is not completely melt.
Detailed description of the invention
Fig. 1 is the flow chart for the heat treatment method that precinct laser fusion of the present invention shapes GH4169 alloy;
Fig. 2 is selective laser melting process schematic illustration of the present invention;
Fig. 3 is the sample schematic diagram of the GH4169 alloy after present invention forming;
Fig. 4 is heat treatment process figure of the present invention;
Fig. 5 is the path of printing of the invention.
Specific embodiment
Below in conjunction with attached drawing, the present invention is described in detail:
The present invention provides a kind of heat treatment method of precinct laser fusion forming GH4169 alloy, can improve because shaping
Due to the segregation phenomena of the too fast generation of cooling rate in journey.Bulk is carried out to homogenize+be dissolved+double aging heat treatment, this processing mode
There can be the hardening constituents such as δ phase γ ' and γ " in material, while interdendritic brittleness Laves phase can be dissolved and make hardening constituent in matrix
Upper disperse educt reduces material notch sensitivity, so that the comprehensive performance of material improves so as to improve the intensity of material.
Bulk sample of the present invention using (SLM) direct forming or can be led to existing metal increases material manufacturing technology
Cross the GH4169 alloy sample of commercially available (SLM) forming.
In the following, being further elaborated on by embodiment and attached drawing to the present invention.However, it is not limited to this, all to this hair
Bright technical solution is modified or replaced equivalently, and without departing from the spirit and scope of the technical solution of the present invention, should all be covered
In protection scope of the present invention.
Embodiment 1
The present embodiment selects NRD-SLM-300 type equipment, and technology schematic diagram as shown in Fig. 2, use in a computer first
SolidWorks establishes the threedimensional model (20mm × 20mm × 20mm square bulk sample) of GH4169 alloy sample, then will
The alloy structure model presses every layer of 25 μ m thick slicing delamination (800 layers), by the 3D shape of every layer of the alloy block structure
Then data conversion determines the track of laser beam flying according to every layer of two-dimensional silhouette data at a series of two-dimensional silhouette data；
High-purity GH4169 powder (ingredient such as table 1) is then placed on feeder.By powdering roller by the GH4169 alloy powder
It is equably laid on the GH4169 substrate of 10mm thickness, GH4169 alloy powder laying depth meets the thickness requirement of layering；Swash
Radiant carries out selective melting, the 3D printing of setting to GH4169 alloyed powder last layer according to the track of determining laser beam flying
Parameter are as follows: laser power 300W, scanning speed 1.3m/s, 150 μm of sweep span, scan path are illustrated in figure 5 scan path
The processing of one layer of GH4169 alloy bulk style is completed in the S type path for being 65 ° for upper and lower phase angle, then passes through powdering roller,
One layer of GH4169 alloyed powder is repaved, then carries out one layer of processing, to repeat shaping a 20mm × 20mm × 20mm just layer by layer
Cube bulk sample is as shown in Figure 3.Blocky sample after forming is scaled off from substrate by wire cutting, then to blocky sample
It homogenized, be dissolved and double aging heat treatment, heat treatment process figure is as shown in Figure 4.Its temperature homogenized is 1030 DEG C, is protected
The warm time is 1h, and 960 DEG C, soaking time is 1 hour air-cooled, and the temperature of double aging processing is 720 DEG C, and soaking time is 8 hours,
620 DEG C then are furnace-cooled to 50 DEG C/h, soaking time is 8 hours, air-cooled.
1 GH4169 alloy composition of table (mass fraction/%)
Claims (1)
1. the heat treatment method of precinct laser fusion forming GH4169 alloy, which is characterized in that the method is swashed using constituency
Light is fused into, and is homogenized, is dissolved and double aging is heat-treated the mode that combines, specifically includes the following steps:
Step 1:
Slicing delamination is carried out to GH4169 alloy bulk sample threedimensional model, every layer of three-dimensional data is converted into 2-D data,
3D printing equipment is imported, 3D printing parameter is set, is shaped using precinct laser fusion, by high-purity GH4169 powder printing-forming
For 20mm × 20mm × 20mm square bulk sample；
The 3D printing parameter of setting: laser power 300W, scanning speed 1.3m/s, 150 μm of sweep span, scan path are upper and lower
Phase angle be 65 ° S type path, face powder 25 μm of thickness；
Step 2: in heat-treatment furnace, step 1 sample is homogenized respectively, be dissolved and double aging heat treatment；At homogenization
Manage process conditions are as follows: temperature control is 1010 ~ 1065 DEG C, keeps the temperature 1h；Solid solution treatment process condition are as follows: be air-cooled to 950 ~ 980 DEG C
Afterwards, 1h is kept the temperature；Double aging heat treatment condition are as follows: be air-cooled to 720 DEG C, keep the temperature 8h；Control 50 DEG C/h cooling velocity, heat treatment
620 DEG C are furnace-cooled to, after keeping the temperature 8h, is air-cooled to room temperature.
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110340361A (en) * | 2019-07-30 | 2019-10-18 | 南京工业大学 | Technological process for quickly and directly manufacturing hot working die |
| CN110523983A (en) * | 2019-09-18 | 2019-12-03 | 燕山大学 | A kind of novel high-performance superfine crystalline substance GH4169 metal worm disc manufacturing method |
| CN111187963A (en) * | 2020-02-14 | 2020-05-22 | 山东大学 | Hastelloy suitable for eliminating selective laser melting forming thermal cracks and method and application thereof |
| CN111360266A (en) * | 2020-03-25 | 2020-07-03 | 华南理工大学 | Selective laser melting forming Inconel718 alloy and heat treatment method thereof |
| CN112191845A (en) * | 2020-09-18 | 2021-01-08 | 中国航发北京航空材料研究院 | Hot processing method for improving structural uniformity of additive manufacturing nickel-based superalloy |
| CN112239838A (en) * | 2019-07-17 | 2021-01-19 | 天津大学 | Heat treatment process method for selective laser melting forming GH4169 |
| WO2021051308A1 (en) * | 2019-09-18 | 2021-03-25 | 西门子股份公司 | Additive manufacturing method and element |
| CN113351881A (en) * | 2021-06-15 | 2021-09-07 | 中国航发成都发动机有限公司 | Mixed additive manufacturing method of aeroengine case |
| CN113927044A (en) * | 2021-09-24 | 2022-01-14 | 南昌航空大学 | Solid solution treatment method for laser additive manufacturing of high-temperature alloy |
| CN115319113A (en) * | 2022-08-12 | 2022-11-11 | 中国航发北京航空材料研究院 | Laser selective melting manufacturing method for aeroengine cyclone casing |
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Cited By (12)
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| CN112239838A (en) * | 2019-07-17 | 2021-01-19 | 天津大学 | Heat treatment process method for selective laser melting forming GH4169 |
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| CN110523983A (en) * | 2019-09-18 | 2019-12-03 | 燕山大学 | A kind of novel high-performance superfine crystalline substance GH4169 metal worm disc manufacturing method |
| WO2021051308A1 (en) * | 2019-09-18 | 2021-03-25 | 西门子股份公司 | Additive manufacturing method and element |
| CN111187963A (en) * | 2020-02-14 | 2020-05-22 | 山东大学 | Hastelloy suitable for eliminating selective laser melting forming thermal cracks and method and application thereof |
| CN111360266A (en) * | 2020-03-25 | 2020-07-03 | 华南理工大学 | Selective laser melting forming Inconel718 alloy and heat treatment method thereof |
| CN112191845A (en) * | 2020-09-18 | 2021-01-08 | 中国航发北京航空材料研究院 | Hot processing method for improving structural uniformity of additive manufacturing nickel-based superalloy |
| CN113351881A (en) * | 2021-06-15 | 2021-09-07 | 中国航发成都发动机有限公司 | Mixed additive manufacturing method of aeroengine case |
| CN113927044A (en) * | 2021-09-24 | 2022-01-14 | 南昌航空大学 | Solid solution treatment method for laser additive manufacturing of high-temperature alloy |
| CN113927044B (en) * | 2021-09-24 | 2023-11-03 | 南昌航空大学 | Solution treatment method for manufacturing high-temperature alloy by laser additive |
| CN115319113A (en) * | 2022-08-12 | 2022-11-11 | 中国航发北京航空材料研究院 | Laser selective melting manufacturing method for aeroengine cyclone casing |
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Application publication date: 20190607 |